EP2669184B1 - Wall installation system and method - Google Patents

Wall installation system and method Download PDF

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Publication number
EP2669184B1
EP2669184B1 EP13168536.4A EP13168536A EP2669184B1 EP 2669184 B1 EP2669184 B1 EP 2669184B1 EP 13168536 A EP13168536 A EP 13168536A EP 2669184 B1 EP2669184 B1 EP 2669184B1
Authority
EP
European Patent Office
Prior art keywords
wall panel
lock
tab
locking
lock strip
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP13168536.4A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP2669184A3 (en
EP2669184A2 (en
Inventor
W. Kwun-Wing Cheung
Mark Cloud
Christopher L. Schwitters
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Boeing Co
Original Assignee
Boeing Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Boeing Co filed Critical Boeing Co
Publication of EP2669184A2 publication Critical patent/EP2669184A2/en
Publication of EP2669184A3 publication Critical patent/EP2669184A3/en
Application granted granted Critical
Publication of EP2669184B1 publication Critical patent/EP2669184B1/en
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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/066—Interior liners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B21/00—Means for preventing relative axial movement of a pin, spigot, shaft or the like and a member surrounding it; Stud-and-socket releasable fastenings
    • F16B21/09—Releasable fastening devices with a stud engaging a keyhole slot
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49826—Assembling or joining
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/53—Means to assemble or disassemble

Definitions

  • the present disclosure relates to wall installation systems, such as for aircraft interior sidewalls. More particularly, the present disclosure relates to a system and method for installing wall panels that is quick and secure and requires minimal tools, and which also facilitates later removal of wall sections while minimizing damage to the wall structure.
  • Document DE 10 2009 031 541 A1 shows a fastening assembly for a fascia part for the interior of a vehicle on a structural part. At least one fastening device is provided that has clipping means on both parts of the fascia part and on the side of the structural part which clip means can be fixed via locking means.
  • Document EP 1 468 907 A2 shows an apparatus and method of attaching panels to support structures.
  • the apparatus includes a first member and second member.
  • the first member is coupled to the support structure and has a first elongated coupling member.
  • the second member has a head portion and a base portion.
  • the head portion has at least one slot dispersed therein that is adapted to receive an edge portion of the panel.
  • the base portion includes a second elongated coupling member that is adapted to be coupled to the first elongated coupling member.
  • Modern commercial aircraft typically include a fuselage having a series of curved transverse ribs and longitudinal stringers.
  • the exterior of the ribs and stringers are covered with a skin of aluminum, carbon fiber composite or other suitable material.
  • the interior of the aircraft includes a series of curved sidewall panels that are attached to the inside of the ribs, typically by screws or other fasteners.
  • the wall panels are typically of polymer material, and can include window frames and other structure that forms a part of the finished aircraft. Once wiring, insulation and other internal wall components are installed between the ribs and inside the skin, the interior wall panels are attached to cover the insulation and other internal wall components, such as environmental components, with a durable covering that provides a pleasing appearance.
  • Typical aircraft sidewall panels require specialized tooling and hardware for installation, such as special screws, washers, screw drivers, panel installation support aids, shims, etc.
  • a sidewall installation involves eight fasteners that attach to their respective frame mounting brackets.
  • Some sidewall systems include mounting hardware (e.g. screws) that is shared between adjacent panels.
  • Other sidewall systems avoid screws and fasteners by using keyways, slotted brackets and the like.
  • Typical sidewall installations can also present challenges when removal of panels is desired.
  • Certain aircraft maintenance and repair operations can involve the removal of one or more sidewall panels in an aircraft, in order to allow access to electrical, mechanical and other components inside the wall.
  • removal of an existing panel presents a higher than desired chance of damage to the panel (perhaps resulting in costly replacement), and a higher than desired likelihood of misalignment or other defect when the panel is replaced.
  • Panel systems that have shared fasteners between adjacent panels present other possible problems.
  • the present disclosure is directed toward one or more of the above-mentioned issues.
  • a system according to claim 1 and a method according to claim 11 is provided.
  • a system for attaching a wall panel including a wall panel, and a lock strip.
  • the wall panel has a back and a tab extending from the back.
  • the lock strip is moveably attached to a wall frame member, and has a three-position locking slot, including a receiving portion configured to receive the tab, a locking portion configured to lock the tab with respect to the frame member, and a release portion configured to release the tab.
  • the wall panel is removably attachable to the frame member by inserting the tab into the receiving portion and linearly moving the lock strip to lock the tab in the locking portion.
  • the system further includes a spline, having a channel, fixedly attached to the frame member, the lock strip being moveably disposed in the channel.
  • the system further includes an insert slot, disposed in the spline, corresponding to a position of the locking slot, to allow passage of the tab into the locking slot.
  • the tab includes a substantially rigid, upstanding member having a distal bulb end configured to engage the receiving portion of the locking slot in a friction fit.
  • the locking portion includes wedge surfaces oriented to lock the tab in the slot in two dimensions.
  • the wall panel is an aircraft interior panel
  • the frame member is a rib of an aircraft fuselage.
  • the system further includes a wedge, extending from the back of the wall panel, and an index retainer, attached to the frame member, configured to releasably receive and support the panel via the wedge upon initial attachment of the panel to the frame.
  • the index retainer provides a mechanical stop for the lock strip when at the locking position.
  • the wall panel is removable from the frame by linearly moving the lock strip to align the release portion with the tab.
  • release portion has a largest size
  • the locking portion has a smallest size of the three-position locking slot.
  • an aircraft having an airframe fuselage with a plurality of substantially parallel frame members, a spline, fixedly attached to the frame members, an interior wall panel, and a lock strip, linearly moveably disposed in the spline.
  • the wall panel has a back, with a plurality of tabs extending from the back.
  • the lock strip has a plurality of three-position locking slots. Each locking slot includes a receiving portion, configured to receive a tab, a locking portion, configured to positionally lock the tab with respect to the frame member, and a release portion, configured to allow removal of the tab from the slot.
  • the wall panel is removably attachable to the frame by linearly moving the lock strip to align the release portion with the tab.
  • the tab comprises a substantially rigid, upstanding member having a distal bulb end configured to engage the receiving portion of the locking slot in a friction fit.
  • the receiving portion, the locking portion and the release portion are substantially linearly aligned, and the release portion has a largest size, and the locking portion has a smallest size of the three-position locking slot.
  • the locking portion includes wedge surfaces oriented to lock the tab in the slot in two dimensions.
  • a method for installing a wall panel in an aircraft fuselage interior includes inserting a plurality of tabs extending from a back of a wall panel into receiving portions of three-position moveable lock strips associated with at least two frame members of the fuselage, and linearly pulling the lock strips to align a locking portion of the locking slot of the lock strip with the tabs, thereby fixing the position of the wall panel with respect to the frame members.
  • the method further comprises adjusting a position of the wall panel prior to linearly pulling the lock strip to lock the wall panel into the fixed position.
  • the step of linearly pulling the lock strips comprises pulling the lock strips downwardly with respect to the wall panel and the frame members.
  • the method further includes linearly pulling the lock strips to align release portions of the lock strips with the tabs, and drawing the tabs out of the release portions while drawing the panel away from the frame members, to remove the wall panel from the frame members.
  • the step of linearly pulling the lock strips comprises pulling the lock strips downwardly with respect to the wall panel and the frame members.
  • FIGs. 1A and 1B Shown in FIGs. 1A and 1B is an aircraft sidewall panel 10 that is ready to be installed in the interior of an aircraft.
  • Aircraft sidewall panels are frequently honeycomb core or crush-core polymer panels, though other materials can also be used, such as aluminum, and it is to be understood that the system disclosed herein is not limited to these materials.
  • this sidewall panel embodiment includes a back surface 14, to which window frames 16 are attached and positioned to align with exterior structural windows 18 in the outer skin of the aircraft.
  • the sidewall panel 10 has a top edge 20, a bottom edge 22, a right edge 24, and a left edge 26 (though these edges appear reversed in the rear view of FIG. 1A ).
  • Adjacent sidewall panels 28 are also visible in FIG. IB.
  • the bottom edge 22 of the wall panel and the bottom edges 30 of the adjacent wall panels are intended to generally align along line 32, which can be parallel with what is called the water line of the aircraft.
  • a series of ventilation panels 34 which extend from the water line down to the aircraft cabin floor 36, and are part of the aircraft ventilation system. These lower panels are sometimes referred to as decompression air grills, and in one embodiment extend about 15" above the floor. These can be installed after the respective sidewall panels above them are installed, as discussed in more detail below.
  • FIG. 1B Shown in FIG. 1B is a perspective view of an embodiment of a sidewall installation system 8.
  • This figure shows the aircraft interior sidewall panel 10 positioned near an aircraft interior frame having multiple parallel frame members 12.
  • the frame members 12 are generally upright, curved ribs of an aircraft fuselage, with a wall installation spline 40 attached to at least some of the frame members.
  • the wall installation system 8 and method disclosed herein can be used with frame members that are curved or straight, and with frame members that are vertical, horizontal, or at any other angle.
  • the curvature of the wall panel 10 can generally match the curvature of the frame members, though the system and method disclosed herein can apply to wall panels that are not curved.
  • the frame members 12 are likely to be of aluminum or composite material (e.g. reinforced carbon fiber).
  • the wall installation system 8 disclosed herein is useful with frame members of many other materials, such as metal, polymer or composite, wood, etc.
  • the tabs 38 can be of strong, resilient polymer material, such as Ultem® (polyetherimide) or PEEK (polyetheretherketone). Other materials can also be used.
  • FIGs. 1B and 2 is the wall installation spline 40 that is attached to the frame members 12.
  • the spline 40 includes a plurality of insert slots 48 for receiving the tabs 38 of the wall panel 10, and a pull tab 98 for locking the tabs to the spline and thus to the frame 12.
  • a lower index retainer 70 is also attached to the frame 12 below the bottom end of the spline 40, and is discussed in more detail below.
  • FIG. 3 An exploded perspective view of this embodiment of a wall installation system 8 is provided in FIG. 3 .
  • the view of FIG. 3 is looking down at the top 45 of the channel 56 and spline 40.
  • the spline 40 is a "T" section structural member having a web 42 and a flange 44.
  • the web of the spline is fixedly attachable to the frame member 12, such as via production shock mounts (not shown) located near the top end 45 and bottom end (47 in FIGs. 5 and 6 ) of the spline 40, supporting the structural spline like a bridge.
  • Shock mounts are well known in the aircraft industry, and those of skill in the art will be able to select and use suitable shock mounts to attach the spline 40 to the aircraft frame member 12.
  • the spline 40 can be attached to the frame 12 at more than two connection locations. Different numbers of connectors can also be used. Using only two connectors helps to reduce the transmission of mechanical noise energy and vibration to the spline by virtue of having fewer mechanical connection points through which vibration can be transmitted, and also reduces weight (since there are fewer connectors), installation time, and the part count of the installation. Alternatively, more connectors can increase the strength of the connection.
  • the spline 40 can be of polymer material, such as Ultem® or PEEK, or it can be of metal, such as aluminum.
  • the interior face 46 of the flange 44 of the spline 40 includes two series' of insert slots 48 on opposing flanges 44, which correspond to positions of tabs 38 on two adjacent wall panels 10, to allow passage of each tab 38 into a respective locking slot, as discussed below.
  • the tabs 38 are substantially rigid, upstanding members with a distal bulb end 54 configured to engage the receiving portion of a locking slot in a friction or snap-in fit, as discussed below.
  • the tabs 38 generally include a base 50, which is attached to the wall panel 10 (e.g.
  • tabs 38 A variety of configurations for the tabs 38 have been considered and tested, and the wall installation system 8 disclosed herein is not limited to the configuration shown in the drawings. For example, tabs having a bulb top 54 with a gap or slot (not shown) for providing spring-like performance upon insertion have been tested. Other configurations can also be used.
  • FIG. 3 is an exploded view, and shows the channel 56 separated from the spline 40, and the lock strip 58 outside of the channel 56, though in actual use these elements will be connected and operate together.
  • the channel 56 can be a separate member that is fixedly attached to the spline 40, as shown in FIG. 3 .
  • the channel 56 can be integrally formed as part of the spline 40.
  • An embodiment of a spline 140 having an integrally formed channel 156 is shown in FIG. 5 .
  • the spline 140 is a "T" section structural member having a web 142 and a pair of flanges 144a, b.
  • the web 142 of the spline is designed to be fixedly attached to the frame member 12 of the aircraft, such as by production shock mounts, as discussed above.
  • the back side of each flange 144 includes an integral channel 156 for carrying a lock strip, as discussed above.
  • the central floor 159 of the channel 156 has side walls 157 that are configured to wrap around and hold the edges of the lock strip 58, allowing it to linearly slide within the channel 156 for locking and unlocking the tabs 38 of the wall panel 10, as described in more detail below.
  • the interior face 146 of each of the flanges 144 of the spline 140 includes a series of insert slots 148 that correspond to positions of locking slots in the lock strip 58 for each channel 156, to allow locking tabs 38 from two adjacent wall panels 10 to insert into the respective slots for locking, as discussed below.
  • the spline 140 with the integral channel 156 can be of polymer, metal, or other suitable materials.
  • the lock strip 58 has a plurality of three-position locking slots 60.
  • Each locking slot 60 is positioned to generally align with one of the insert slots 48 of the spline, as discussed above.
  • the locking slot 60 has three different sections or portions that vary in width, and is configured to receive the tabs 38 that are mounted on the back side of the sidewall panels.
  • the lock strip 58 is of 4-6 ply fiberglass phenolic material, which is tough and resilient, and interlocks well with the polymer tabs 38. Other materials can also be used.
  • FIGs. 10-14 Various views of the channel 56 and lock strip 58 are shown in FIGs. 10-14 .
  • the lock strip 58 is linearly moveable in the channel 56, as indicated by double arrow 61 in FIGs. 6 , 7B , 9 and 12-14 .
  • Each locking slot 60 includes a receiving portion 62 which is the lowest portion of the locking slot 60, a locking portion 64 in the middle, and a release portion 66 at the upper end of the locking slot.
  • the locking portion 64 is the narrowest, while the release portion 66 is the widest, and the receiving portion 62 is between the two with respect to width.
  • the receiving portion 62 is configured to receive the tab 38 in a friction fit or "snap" fit.
  • Both the tabs 38 and the lock strip 58 can be of resilient polymer material, which is somewhat flexible and pliable. Other materials can also be used.
  • the receiving portion 62 has a width that is slightly narrower than the distal bulb 54 of the tab 38. This allows the distal bulb 54 to be pushed into the receiving portion 62 in a press fit that can hold the wall panel 10 in rough position, before it is locked into place. This allows the position of the wall panel 10 to be adjusted slightly after it is initially attached to the wall frame members 12.
  • the channel 56 can be slightly wider than the lock strip 58 (e.g.
  • the press-fit configuration of the tabs 38 and the receiving portion 62 allows any of the tabs 38 to be pulled back out of their respective receiving portions 62 if desired, such as for repositioning of the wall panel, etc., without damaging the wall panel, tabs or splines 40.
  • the tabs are more easily removed if the lock strip 58 is pulled to its release position, as shown in FIG. 14 and described below.
  • the size and configuration of the tabs 38 and bulbs 54 with respect to the receiving portions 62 are selected to make insertion easy, but extraction not as easy. This helps prevent the wall panel 10 from falling away from the frame 12 after initial insertion of the tabs 38. This feature is provided in part by the configuration of the lock strip 58 and the channel 56.
  • the force pushing the tab can temporarily deform the lock strip 58 away from the channel (since the lock strip is flexible), thus allowing the rounded distal surface of the bulb 54 of the tab 38 to deform the receiving portion 62 and allow entrance of the tab.
  • the back side of the bulb 54 (which is not as rounded as the distal end of the bulb) is not as capable of deforming and pushing back through the receiving portion 62.
  • the lock strip is directly supported against force in the opposite direction by the floor 59 of the channel 56, and by the spline 40. This dramatically reduces the degree of flexibility of the lock strip, 58 making it more difficult to remove a tab 38 from the receiving portion 62 than it is to insert the tab in the first place.
  • FIG. 4 is a perspective view of an embodiment of an upper alignment device 68 for receiving the top edge 20 of a wall panel 10.
  • the upper alignment device 68 can be a separate channel device attached to the frame 12, or it can be, for example, a strong back of an overhead stowage bin 67, which can include an elongate slot 69 that is configured to perform the same function.
  • One upper alignment device 68 can be shared to receive the top edges 20 of two or more adjacent sidewall panels 10. Indeed, a substantially continuous upper alignment device 68 can extend for a long distance between a row of overhead storage bins 67 and the adjacent side frame structure 12 of an aircraft, providing an alignment reference for a series of adjacent wall panels 10.
  • the snap-in retaining feature of the receiving portion 62 of the lock strip 58 does not merely perform a snap-in and snap-out function. Snap-in and snap-out devices can tend to break or become damaged with even limited usage, and the likelihood of damage increases depending on the strength of the fit. For an aircraft sidewall application, it is desirable that a snap-in and snap-out device have strength comparable to a traditional screw fastener. This is difficult to achieve without producing a configuration that is highly susceptible to damage.
  • the snap-in attachment system disclosed herein provides easy engagement of the panel 10 to its mating part - the locking slot 60. Because the lock strip 58 is linearly slidable, the locking slot 60 is not stationary, and moves when the lock strip 58 is pulled down (or pushed up, as discussed below) as indicated by arrow 61. When a worker begins installation of a wall panel 10, the worker can first get the top two tabs 38 (e.g. one at upper left and one at upper right of the panel 10) to snap into their respective receiving portions 62. This becomes a primary installation index. This initial engagement will keep the sidewall panel loosely attached (i.e. hanging in place) on the spline 40, and thereby upon the frame members 12.
  • tabs 38 can then be blind-pushed into their corresponding receiving portions 62 without interference. In this way, all tabs 38 of a given wall panel 10 can be snapped into their respective locking slots 60 and initially kept in place, before they are locked. In one embodiment, there are eight snap-in tabs 38 per sidewall panel 10, though other numbers of tabs can be used. Under non-locking status, the sidewall panel 10 is allowed to have a level of adjustment for window alignment. With all attachments set, adjusting window alignment or other alignment aspects of the panel is greatly simplified.
  • the top edge 20 of the sidewall panel 10 When a worker slides the top edge 20 of the sidewall panel 10 up into the upper alignment device 68 during installation, the top edge 20 of the panel will be caught in place, and stopped from further advancement or moving upward. This guides the installer to place the sidewall 10 in an appropriate position before the next step. At this point, the sidewall 10 can be moved or adjusted, as desired, to find access for the top left and right tabs 38 to snap into their receiving portions 62, as discussed above. Once engaged, the upper alignment device 68 becomes a retainer, keeping the top edge 20 of the sidewall from moving inboard or outboard.
  • FIGs. 2 , 6 , 80 in FIGs. 7A, B Initial attachment and alignment of a wall panel 10 is also facilitated by a lower index retainer assembly (70 in FIGs. 2 , 6 , 80 in FIGs. 7A, B ) associated with the lower end of the panel 10.
  • the lower index retainer assembly essentially provides a pin connection at the lower left and right sides of the panel 10 for facilitating initial placement of the panel.
  • a perspective/sectional view of an embodiment of a lower index retainer assembly 70 is shown in FIG. 6
  • two views of another embodiment of a lower index retainer assembly 80 are provided in FIGs. 7 and 8 .
  • the lower index retainer functions to set the bottom edge 22 of the sidewall 10 at the designated water line level (32 in FIGs. 1B and 6 ) during initial wall placement, so as to give a general right height and position of the panel 10, and to help provide an initial attachment of the wall before the lock strip 58 is locked.
  • the first type of lower index retainer 70 includes a retainer clip 72, which is attached to the air frame 12, such as via a production shock mount.
  • a snap-in wedge 76 is attached to the wall panel 10.
  • an individual wall panel 10 can have two snap-in wedges attached near the bottom edge 22.
  • the lock strip 58, channel 56 and spline 40 of the wall attachment system 8 are also visible in the view of FIG. 6 .
  • the lower index retainer assembly 70 is a passive, one-piece retainer device that is configured to capture the snap-in wedge 76 from the lower region of the sidewall panel 10.
  • the lock strip 58 includes a vertical slot 78 that allows the snap-in wedge 76 to pass through the lock strip to reach the retainer clip 72.
  • a close-up view of one embodiment of a snap-in wedge 76 is shown in FIG. 8A .
  • the snap in wedge 76 generally includes a pointed distal end 77, a bottom edge 79, and an upper slot 74.
  • the retainer clip 72 includes a resilient upper clip member 73, which snaps into the upper slot 74 of the wedge 76 when the wedge is inserted into the clip.
  • the clip 72 also includes a lower support shelf 75, which supports the bottom 79 of the wedge 76, thereby supporting the wall panel 10 when the wedge is inserted.
  • FIGs. 7A and 7B A second type of lower index retainer assembly 80 is shown in FIGs. 7A and 7B . It is to be understood that the lower index retainer configurations of either FIG. 6 or FIGs. 7A-B can be used with the wall panel attachment system 8 shown and described herein. Other configurations can also be used.
  • the embodiment shown in FIGs. 7A and 7B includes an index retainer body 82 that is designed to be attached to the airframe 12 below the bottom edge of the spline (40 in FIG. 6 ), at a similar position and orientation as the lower index retainer embodiment 72 shown in FIG. 6 and discussed above.
  • the index retainer body 82 includes a forward slot for receiving the snap-in wedge 76, an upper clip member 83 that interlocks with the wedge 76, in the manner discussed above, and a spring-loaded slide block 84 disposed below the snap-in wedge 76.
  • the lock strip 58 includes a slot 78 for allowing passage of the wedge 76, and also includes a slot frame 85 having slot edge bumpers 86 that extend outward from the slot frame 85. A close-up view of these bumpers is shown in FIG. 7B .
  • the bumpers 86 are positioned alongside the central extent of the slot 78, and are designed to contact the top surface of the slide block 84 when the lock strip 58 is at the locking position. This stops the lock strip 58 from moving further down, keeping it at full locking position, but without going beyond that position.
  • the snap-in wedge 76 and the slot edge bumpers 86 can also be configured to provide additional interlocking structure to hold the wall panel in place.
  • the body of the snap-in wedge 76 can include vertical ridges 81. While only one side of the snap-in wedge 76 is shown in FIG. 7A , similar ridges can be provided on the opposite side, also. These ridges 81 can be configured to interlock with similar vertical ridges 83 that are provided on the interior faces of the lock strip slot edge frame bumpers 86, as shown in FIG. 7B .
  • the ridges 83 on the inside of the bumpers 86 will intermesh with the ridges 81 on the outside of the snap-in wedge 76, thus providing additional locking force to hold the wall panel 10 in place.
  • the snap-in wedges 76 and bumpers 86, with the ridges 81 and 83, can thus be viewed as a slightly different and larger version of the interlocking tabs 38 and their associated locking structure.
  • the slide block 84 also includes a downwardly extending release tab 87 at its rear extremity, and a sloped surface 88 on the underside of its forward end.
  • the release tab 87 is used to push the slide block back, away from the lock strip 58, thereby withdrawing the forward portion of the slide block from contacting the bumpers 86, thereby allowing the lock strip 58 to be drawn downward for releasing the wall panel 10, in the manner discussed below.
  • the backwardly extended position of the slide block 84 is shown in dashed lines at 89 in FIG. 7B . Biasing of the slide block toward the forward locking position can be accomplished with a spring element 90, which can be metal, polymer or other suitable material, and can be configured in various ways.
  • the sloped bottom surface 88 of the slide block 84 provides a wedge surface to allow the bumper 86 to push the slide block aside (against the biasing force upon the slide block) when the lock strip 58 is pushed upwardly, similar to the way a door latch is naturally pushed aside when the angled and/or curved latch face contacts a strike plate when a door is closed.
  • the length of the slot 78 allows the lock strip 58 to be in an upper position, shown in dashed lines at 92, when the snap-in wedge 76 is first inserted.
  • This position can correspond to the alignment of the receiving portions 62 with the spline insert slots 48 for initial insertion of the tabs 38 (see FIG. 12 ).
  • the lock strip 58 will be in the position shown in FIG. 7B when the lock strip is pulled downward to the locking position, which can correspond to the lock strip 58 having the locking portion 64 aligned with the tabs 38 to lock the wall panel 10 in place (see FIG. 13 ).
  • lock strip 58 can be pulled to the fully down release position, shown at 93 in FIG. 7B , after the slide block 84 is withdrawn, to align the release portion 66 with the spline insert slot 48 and allow removal of the tabs 38 and the wall panel 10 (see FIG. 14 ).
  • Contact of the top inside surface of the slot 78 with the top edge of the snap-in wedge 76 can serve to define the maximum downward extent of travel of the lock strip.
  • the lower index retainer 80 and the lock strip 58 with the slot frame 85 and bumpers 86 create a mechanical stop for the locking position of the lock strip through contact of the bumpers 86 with the slide block 84, and the extent of the slot 78 and position of the snap-in wedge 76 define the release position of the lock strip.
  • FIGs. 7A and 7B that governs or restricts the upper position (shown at 92 in FIG. 7B ) of the lower lock strip slot 78 when there is no snap-in wedge 76 inserted through that slot and received in the lower index retainer 80.
  • FIG. 9 which shows the top end 45 of the channel 56
  • this upper position can be governed by a reset stop 94 positioned at the top of the lock strip channel 56.
  • the reset stop 94 in this embodiment includes an end wall 95 and a stop tab 96 that is biased downward to contact or nearly contact (e.g. 0.03" above) the floor 59 of the channel 56.
  • the stop tab 96 includes a tab face 97 that is positioned to contact and receive a boss or ridge 99 on the upper end of the lock strip 58 when it is pushed to this upper position.
  • the lock strip 58 can then be pushed fully upward to the reset position, at which point the top edge of lock strip 58 will bump against face 95 and stop.
  • the ridge 99 of the lock strip 58 will contact the tab face 97 and push the stop tab 96 upward, allowing the ridge 99 to pass under and beyond the tab and then be held in place by the tab 96 as it springs back to its biased position, as shown in FIG. 9 .
  • the receiving portions 62 of the lock strip 58 will again be aligned with the insert slots 48 of the spline 40, ready for insertion of the tabs 38.
  • the sidewall panel 10 will be generally kept in place but not securely locked in a finished position. It can be shifted around a bit for window alignment, or removed from the frame 12 by pulling the lock strip 58 all the way down, if desired.
  • the lower index retainers 70, 80 also allow a certain degree of left-right and up-down sidewall movements for window alignment.
  • the wall panel 10 is held in place while the lock strip 58 is drawn down within the channel 56, so that the locking portion 64 of the locking slot 60 draws down around the tab 38 to lock the tab (and hence the wall panel 10) with respect to the frame member 12.
  • the lower index retainer 80 of FIGs. 7A and 7B pulling the lock strip 58 down to the locking position will bring the lower ends of the slot frame bumpers 86 into contact with the top of the slide block 84, and thereby provide a mechanical block to further motion.
  • the lock strip 58 includes a pull tab 98 at its lower extremity, which extends below the bottom edge 22 of the wall panel 10.
  • a user can grasp this pull tab 98 (visible in FIGs. 2 , 3 and 6 ) either manually or with a tool, and pull downwardly, so that the lock strip 58 slides downwardly in its channel 56. This draws the respective receiving portion 62 of the lock strip downward so that the respective tab 38 slides into the adjacent locking portion 64 of the lock strip.
  • the region below the bottom edges 22 of the wall panels 10 can be configured to be covered by removable ventilation panels 34, which cover the pull tabs 98 of the lock strips 58 after the installation of the wall panels 10.
  • the locking portion 64 of the lock strip 58 includes wedge surfaces that are configured to lock the tab 38 in the locking portion 64 in two dimensions. Specifically, as shown in FIGs. 11-14 , the locking portion 64 includes side walls 100, which draw laterally close together, like a pair of wedges, in order to bear against opposing sides of the stem portion 52 of the tab 38. This helps to positionally lock the tab with respect to the frame member 12 in the lateral direction (lateral relative to the orientation of the tab 38, fore and aft with respect to the aircraft).
  • the locking portion 64 also includes a pair of uprising rims 102 on opposing sides of the locking slot 60, which bear against the underside of the distal bulb portion 54 of the tab, and thus provide wedge action that applies axial tension on the tab 38, tending to pull it further through the insert slot 48, thus drawing the wall panel 10 snugly against the spline 40 and positionally locking the tab 38 and the wall panel 10 to the spline 40 and thus to the frame member 12 in a friction lock. This secures the wall panel against the frame members 12.
  • the release portion 66 of the lock strip is wider than the receiving portion 62, and does not hold the bulb 54 in a press fit or friction fit. Instead, because of the size of the release portion 66, the tab 38 merely rests loosely in the release portion, allowing the wall panel 10 to be easily removed from the frame members 12 when the lock strip is at this position. At the same time, the tabs 38 within the release portions 66, though loose, will still support the wall panel vertically, and thus prevent the wall panel from simply falling from the frame.
  • This configuration of the locking slot 60 allows free removal of the tabs 38 from the release portion 66, allowing a worker to easily remove the wall panel from the frame, in a controlled and safe manner.
  • the top edge 20 of the panel 10 will also be held in the upper alignment device 68, which will also help prevent the panel from falling away from the frame 12 when the lock strip 58 is pulled to the release position.
  • each of the wedge elements 76 are removed from their respective lower index retainers 70, 80.
  • the lower index retainers 70, 80 thus help to horizontally and vertically support the wall panel 10 in position after all tabs 38 have been released, allowing a single worker to easily remove the entire panel 10, while preventing the panel from simply falling away from the wall frame 12 when the tabs have been released. After a wall panel 10 has been removed, it can be easily reattached in the manner discussed above, without damage to the wall panel 10 or other structure, and without compromising the strength of the connection.
  • a worker can push the lock strip 58 upward (e.g. from the bottom) until it stops against the reset stop 94, as discussed above with respect to FIG. 9 .
  • the lock strip 58 is relatively flexible and may not ordinarily function under axial compression, it can be pushed because it is laterally constrained within the channel 56 of the spline 40.
  • the bumpers 86 move upward and pass through the lower index retainer 80 during this action, the bumpers 86 will contact the sloped bottom surface 88 of the spring-loaded slide block 84 while moving up, and push the slide block 84 aside.
  • the slide block 84 will snap back to its forward position, producing an audible click sound.
  • This click in combination with the mechanical stop and hold provided by the reset stop 94, can confirm the reset to the worker.
  • the receiving portions 62 of the locking slots 60 will be aligned with the insert slots 48 of the spline 40, and thus will be in position for snap-in reinsertion and attachment of the wall panel 10 in the manner explained above.
  • Embodiments of the disclosure may be described in the context of an aircraft sidewall installation method 200 as shown in FIG. 15 and an aircraft 202 as shown in FIG. 16 .
  • exemplary method 200 may include moving the lock strip to the receiving (or fully up) position 204 to prepare for receipt of a wall panel, and then inserting the top tabs 206.
  • the term "receiving position" is used herein to denote the position of the lock strip 58 at which the receiving portion 62 of the locking slot 60 is aligned with the insert slot 48 of the spline 40, and is ready to receive the tabs 38.
  • the remaining tabs can be pushed into place 208 after which the snap-in wedges can then be inserted into their respective lower index retainers 210.
  • Steps 206-210 taken together constitute the overall step of inserting a plurality of tabs extending from the back of a wall panel into receiving portions of a three-position moveable lock strip.
  • the worker can adjust the position of the wall panel 212, such as to center the window structure, etc., and then pull the lock strip to the locking position 214.
  • this involves linearly pulling the lock strip 58 to align the locking portion 64 of the lock strip with the tabs 38, thereby fixing the position of the wall panel with respect to the aircraft frame members.
  • the term "locking position” is used herein to denote the position of the lock strip 58 at which the locking portion 64 of the locking slot 60 is aligned with the tab 38. At this point, the wall panel is locked in place.
  • the exemplary method 200 shown in FIG. 15 also shows the steps in removing a wall panel.
  • a worker first releases the lower index retainer 216, and then pulls the lock strip fully down to the release position 218.
  • release position is used herein to denote the position of the lock strip 58 at which the release portion 66 of the locking slot 60 is aligned with the tab 38.
  • the worker can remove the wall panel 220 from the structure.
  • the worker can then return to the first step and adjust the lock strip to the receiving position 204.
  • a system integrator may include without limitation any number of aircraft manufacturers and major-system subcontractors; a third party may include without limitation any number of venders, subcontractors, and suppliers; and an operator may be an airline, leasing company, military entity, service organization, and so on.
  • the aircraft 202 produced by exemplary method 200 may include an airframe 222, including a fuselage, with a plurality of systems 224 and an interior 226.
  • high-level systems 224 include one or more of a propulsion system 228, an electrical system 230, a hydraulic system 232, and an environmental system 234. Any number of other systems may be included.
  • an aerospace example is shown, the principles of the invention may be applied to other industries, such as the automotive industry.
  • the wall panel installation system includes multiple splines 236, which are attached to the fuselage frame, with lock strips 238 slidably attached to the splines 236.
  • the lock strips 238 each include a three-position locking slot 240, including a receiving portion 242, a locking portion 244 and a release portion 246.
  • wall panels 248 that include tabs 250, these tabs being configured to insert into the receiving portion 242 of the locking slot 240, and be locked into place by movement of the lock strip 238, as discussed above.
  • Apparatus and methods embodied herein may be employed during any one or more of the stages of the sidewall installation method 200.
  • components or subassemblies corresponding to method 200 may be fabricated or manufactured in a manner similar to components or subassemblies produced while the aircraft 202 is in service.
  • one or more apparatus embodiments, method embodiments, or a combination thereof may be utilized during production, for example, by substantially expediting assembly of or reducing the cost of an aircraft 202.
  • apparatus embodiments, method embodiments, or a combination thereof may be utilized while the aircraft 202 is in service, for example and without limitation, during maintenance and service.
  • This wall panel attachment system 8 provides a simple, snap-in design, which allows sidewall panels 10 to push in and snap, keeping the sidewall panel in place without initially being locked. Before final locking of the sidewall panels, the worker can make appropriate adjustments for window alignment, etc. To lock the panels in place, the worker pulls the lock strip 58 down to lock at once all attaching devices that are associated with a single lock strip, without the need for additional hardware or tooling. Once the panels are locked in place, their position is securely fixed without the need for screws, washers, other fasteners.
  • installation and removal of these wall panels 10 can be accomplished by a single worker, without additional parts, fasteners or tooling.
  • the installation and removal process is also very quick. It has been found that installation or removal of a sidewall according to this design can be routinely accomplished in half a minute or less. More specifically, it has been found that installation of a sidewall panel can be accomplished in about 20 seconds or less by a single worker without significant risk or expectation of system deformation or gaps. The steps of attaching or removing a wall panel have each been found to take about 10 seconds or less using this system. When attaching the wall panel, alignment with adjacent panels and adjustment and centering of the sidewall to a structural window can add another 10 seconds to the process.
  • This system and method thus offers a simple and secure sidewall installation.
  • it reduces the number of structural attachments to the airframe from eight to three, and reduces the use of shock-mount brackets and related spacers. It can help speed sidewall installation and improve aircraft production rates during manufacture. It also saves time and expense for aircraft users by reducing the time and labor that is typically involved in regular airplane mandatory checks and maintenance procedures that involve sidewall removal, and helps reduce damage and wear to panels that can often result from removal and reinstallation.
  • wall panel installation system 8 is not limited to use in aircraft.
  • a wall panel installation system and method as disclosed herein can be used for room dividers, where removable panels are desired.
  • This system and method could also be used for automotive interiors and cabinetry, for example, where it is desirable to hide equipment behind a panel, and yet be able to remove the panel for maintenance, if desired.
  • Those of skill in the art will recognize that other applications are also possible.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Connection Of Plates (AREA)
  • Finishing Walls (AREA)
EP13168536.4A 2012-05-31 2013-05-21 Wall installation system and method Active EP2669184B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/485,720 US8979027B2 (en) 2012-05-31 2012-05-31 Wall installation system and method

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EP2669184A2 EP2669184A2 (en) 2013-12-04
EP2669184A3 EP2669184A3 (en) 2016-05-25
EP2669184B1 true EP2669184B1 (en) 2019-07-10

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US (1) US8979027B2 (ko)
EP (1) EP2669184B1 (ko)
JP (1) JP6129644B2 (ko)
CN (1) CN103448900B (ko)
BR (1) BR102013012939B1 (ko)
CA (1) CA2814452C (ko)
ES (1) ES2750039T3 (ko)

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102011009815A1 (de) * 2011-01-31 2012-08-02 Airbus Operations Gmbh Flugzeuginterieurkomponentensystem und Verfahren zur Montage eines Interieurkomponentensystems in einem Flugzeug
DE102014215661A1 (de) 2014-08-07 2016-02-11 Airbus Operations Gmbh Flugzeuginnenverkleidungsbauteil, Verfahren zur Herstellung eines Flugzeuginnenverkleidungsbauteils und Flugzeugbaugruppe
US9682763B2 (en) 2015-05-12 2017-06-20 The Boeing Company Apparatus and methods for attaching panels to support structures
US10137975B2 (en) * 2016-04-06 2018-11-27 The Boeing Company Sidewall mounting hardware for aircraft
US10279887B2 (en) 2016-06-06 2019-05-07 The Boeing Company Decompression panel assembly and methods of assembling the same
US10399660B2 (en) * 2016-06-06 2019-09-03 The Boening Company Decompression panel assembly and methods of assembling the same
WO2018183750A1 (en) * 2017-03-30 2018-10-04 C&D Zodiac, Inc. Sidewall panel assembly
EP3746611A1 (en) 2018-02-01 2020-12-09 Oldcastle Buildingenvelope Inc. Demountable wall system and method
US11548613B2 (en) * 2019-06-27 2023-01-10 The Boeing Company Air grille panel assembly, system, and method of installing the same in a vehicle
CN110844042B (zh) * 2019-10-11 2022-09-30 中国直升机设计研究所 一种集成通风排水功能的口盖
CN114194372A (zh) * 2021-11-05 2022-03-18 中国商用飞机有限责任公司 用于飞机的地板排水组件、具有地板排水组件的飞机以及地板排水组件的布置方法
US20230166826A1 (en) * 2021-11-29 2023-06-01 The Boeing Company Vehicle cabin sidewall-to-floor coupling assembly and method of assembly

Family Cites Families (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1940969A (en) * 1928-10-06 1933-12-26 Woodall Industries Inc Wall panel
US1942119A (en) * 1932-04-11 1934-01-02 George E Gagnier Securing trim panel
US1965520A (en) * 1933-03-20 1934-07-03 Scovill Manufacturing Co Panel fastener
US1948462A (en) * 1933-03-21 1934-02-20 Scovill Manufacturing Co Panel fastener
US2070839A (en) * 1934-07-13 1937-02-16 George E Gagnier Running board assembly
US2925050A (en) 1957-01-09 1960-02-16 Pullman Inc Side frame construction and finish
US3752553A (en) * 1971-07-29 1973-08-14 Amerock Corp Drawer with snap-on front panel
JPS5735127U (ko) * 1980-08-07 1982-02-24
DE3528316A1 (de) 1985-06-26 1987-01-02 Hunter Douglas Metalldecken Pr Tragschienenprofil fuer verkleidungen
US4799631A (en) 1987-02-18 1989-01-24 Atr International, Inc. Aircraft shell module
US5202172A (en) * 1991-05-20 1993-04-13 General Motors Corporation Molding and retainer assembly
JPH06305489A (ja) * 1993-04-27 1994-11-01 Mitsubishi Heavy Ind Ltd 内装・防音断熱部材取付方法
US5458521A (en) * 1994-07-05 1995-10-17 Union Camp Corporation Combination storage container and educational toy
FR2738025B1 (fr) 1995-08-23 1997-11-07 Filippo Agostini Dispositif d'agrafage de pierres et carrelages pour revetement de facade d'immeuble d'habitation et industriel
JP3675630B2 (ja) * 1998-02-06 2005-07-27 株式会社日立製作所 鉄道車両
US6224339B1 (en) * 1998-07-08 2001-05-01 Allison Advanced Development Company High temperature airfoil
US6158690A (en) * 1998-10-30 2000-12-12 Sikorsky Aircraft Corporation Cabin interior panel system for reducing noise transmission in an aircraft
EP1172500B1 (en) 2000-07-14 2005-03-30 Eurogramco SL A cladding system
US6701678B1 (en) * 2001-05-18 2004-03-09 Rubbermaid Incorporated Modular storage enclosure
FR2829102B1 (fr) * 2001-09-06 2004-08-06 Eurocopter France Ensemble structurel d'une partie d'un aeronef et aeronef,en particulier un aeronef a voilure tournante, comportant un tel ensemble structurel
EP1338719B1 (en) 2002-02-14 2009-09-16 Eurogramco SL Cladding system for building walls
US20040190985A1 (en) * 2003-03-27 2004-09-30 Ali Aigner Fixing system
ES2230952B1 (es) * 2002-08-02 2006-07-16 Maria Alarcon Lopez Dispositivo para el ensamblaje de muebles.
US6712316B2 (en) * 2002-08-01 2004-03-30 The Boeing Company Snap-on sidewall assembly
US6871822B2 (en) 2003-04-18 2005-03-29 The Boeing Company Apparatus and methods of attaching panels to support structures
US7429015B2 (en) * 2004-12-20 2008-09-30 Sikorsky Aircraft Corporation Acoustic absorption blanket mounting system for an aircraft cabin
FR2891239B1 (fr) * 2005-09-28 2009-04-17 Airbus France Sas Panneau de plancher et installation pour la fixation d'elements d'amenagement comportant de tels panneaux
US7527223B2 (en) * 2006-04-06 2009-05-05 The Boeing Company Interior panel attachment system
DE102006017241B4 (de) * 2006-04-12 2017-11-23 Airbus Operations Gmbh Ebene Spaltabdeckung für Kabinenverkleidungen
DE102007032233B4 (de) * 2007-07-11 2014-07-10 Airbus Operations Gmbh Installationssystem für ein Flugzeug
DE102009031541A1 (de) * 2009-07-02 2010-02-11 Daimler Ag Befestigungsanordnung eines Verkleidungsteils für einen Innenraum eines Kraftwagens an einem tragenden Bauteil
DE102010038823B4 (de) * 2010-08-03 2017-03-09 Airbus Operations Gmbh Verkleidungsanordnung sowie Luft- oder Raumfahrzeug

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
BR102013012939A2 (pt) 2015-06-09
CN103448900A (zh) 2013-12-18
BR102013012939B1 (pt) 2021-07-20
JP2013249056A (ja) 2013-12-12
CA2814452C (en) 2016-07-19
EP2669184A3 (en) 2016-05-25
EP2669184A2 (en) 2013-12-04
CN103448900B (zh) 2017-04-26
US8979027B2 (en) 2015-03-17
CA2814452A1 (en) 2013-11-30
US20130320140A1 (en) 2013-12-05
JP6129644B2 (ja) 2017-05-17
ES2750039T3 (es) 2020-03-24

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